GB1296378A - - Google Patents

Abstract

1296378 Turbomachine blades; gas turbine plant GENERAL MOTORS CORP 5 June 1969 28611/69 Heading F1G, FIT A high temperature turbomachine includes a row of fluid directing airfoil members exposed during operation to hot motive fluid, each airfoil member being hollow to define an internal cavity which is divided by walls extending spanwise of the cavity into three passages, one adjacent each of the leading and trailing edges with an intermediate passage, means for distributing a coolant fluid into the leading edge and intermediate passages at one end of the airfoil member, means connecting these passages to the trailing edge passage at the other end of the airfoil member, and means to provide an outlet for the coolant fluid at said one end of the airfoil member. In the turbojet engine shown in Fig.3, cold liquefied fuel is supplied by fuel supply pipes (not shown) to an annular manifold 26 from which it flows through passages 51, 52 in the turbine nozzle vanes 13 in one direction and in a passage 53 in the opposite direction. The passages 51, 52, 53 are formed in each hollow vane 13 by webs 47, 49 extending spanwise of the vane, the web 47 being adjacent the leading edge and the web 49 approximately at the mid-chord of the vane. The heated fuel then passes to fuel outlet pipes (not shown). Circulation of cooling fuel to the turbine rotor 14 is effected through struts 18 which extend across the exhaust duct, each strut 18 being of doublewalled construction and the fuel flowing through the space 55 between the walls to one or more fuel pipes and then to a manifold (not shown) on the turbine axis. From the manifold, the fuel flows radially outwardly between the forward face of the turbine wheel 64 and a shroud 105 to enter the space between the outer diameter of the wheel and the turbine blade platforms through discharge holes (not shown). The fuel in this space flows through metering orifices 123 or 125 into passages 121 or 126 in the turbine blades 63. These passages, formed by walls 119, 127 extending spanwise of the blades 63, connect at their radially outer ends with a third passage 129 through which the fuel flows, the fuel then flowing radially inwardly between the rear face of the turbine wheel 64 and a shroud 94 to pass via the central passages of the struts 18 to the fuel outlet pipes. The fuel is supplied by suitable pumping means which puts it under sufficient pressure for circulation. The fuel, which may be vaporized in cooling the engine, is supplied by the fuel outlet pipes to the combustion apparatus of the engine.